EP2270397A1 - Chambre de combustion de turbine à gaz et turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz et turbine à gaz Download PDF

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Publication number
EP2270397A1
EP2270397A1 EP09162305A EP09162305A EP2270397A1 EP 2270397 A1 EP2270397 A1 EP 2270397A1 EP 09162305 A EP09162305 A EP 09162305A EP 09162305 A EP09162305 A EP 09162305A EP 2270397 A1 EP2270397 A1 EP 2270397A1
Authority
EP
European Patent Office
Prior art keywords
wall
gas turbine
turbine combustor
combustion chamber
composite
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP09162305A
Other languages
German (de)
English (en)
Inventor
Christoph Buse
Alessandro Casu
Giacomo Colmegna
Werner Stamm
Stefan Völker
Ulrich Wörz
Adam Zimmermann
Tilman Auf Dem Kampe
Jaap Van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP09162305A priority Critical patent/EP2270397A1/fr
Publication of EP2270397A1 publication Critical patent/EP2270397A1/fr
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the present invention relates to a gas turbine combustor having a substantially rotationally symmetrical cross section and at least one axial section, which has an inner wall with an outer side and an outer wall with an inner side facing away from the inner wall and spaced from the inner side, so that between the outer side and the Inside a at least one cooling fluid channel forming space is present.
  • the present invention relates to a gas turbine.
  • a gas turbine comprises as essential components a compressor, a turbine with blades and guide vanes and at least one combustion chamber.
  • the blades of the turbine are arranged on a shaft extending mostly through the entire gas turbine, which is coupled to a consumer, such as a generator for power generation.
  • the shaft provided with the blades is also called turbine runner or rotor
  • combustion chambers of so-called diffusion combustion systems in which a fuel-rich fuel-air mixture is burned, are exposed to very high temperatures during operation of the gas turbine.
  • the combustion chamber is in this case a mechanical container, which serves to stabilize the flame and to ensure the transfer of the heated by the combustion compressor cooling air K in the turbine. Since this mechanical container is located near the flame, it is exposed to temperatures that exceed even the melting temperature of superalloys. Therefore, in order to prevent the combustion chambers from melting, they are often equipped with complex double-walled cooling systems and cooling fins between the walls.
  • a combustion chamber for a diffusion flame, which has a double wall, is, for example, in WO 99/17057 A1 described.
  • the first object is achieved by a gas turbine combustor according to claim 1, the second object by a gas turbine according to claim 11.
  • the appended claims contain advantageous embodiments of the invention.
  • a gas turbine combustor according to the invention has a substantially rotationally symmetrical cross-section and has at least one axial section which has an inner wall with an outer side and an outer wall with an inner side facing the inner wall and spaced from the inner side.
  • a gap forming at least one cooling fluid channel.
  • the inner wall is at least partially made of composite.
  • the composite may partially comprise an envelope, e.g. made of metal.
  • the composite inner wall has the advantages of being much faster than the planed fins used in the prior art. Another advantage is that the heat transfer is increased and thus has a more efficient cooling as a result.
  • the composite is metallic or ceramic. This has the necessary temperature resistance.
  • the composite is formed as a foam. This has several advantages.
  • a disadvantage of using the planed cooling fins customary in the prior art is namely that the inner wall of the combustion chamber undergoes a significant radial thermal expansion due to the very high temperatures prevailing during operation. This thermal expansion is large enough to reduce the flow area through the space between the inner wall with the prior art cooling fins and the outer wall. reason for this is that the cooling fins bring about no rigidity of the inner wall, which would oppose a radial expansion of the inner wall.
  • the inner wall is given a stiffness, which precludes a radial expansion.
  • Straight metal or ceramic foam is characterized by a particularly high rigidity.
  • foams have the advantage that it is easy to work and thus again contributes to the simplified production.
  • foams have a high temperature resistance. They can therefore be used in combustion chambers.
  • Metal or ceramic foam also has a good acoustic property.
  • the inner wall made of foam can also be used to dampen combustion chamber vibrations, e.g. by means of mounted in the wall cooling holes that can serve as a sound absorber.
  • the foam texture e.g. large or small pores on different areas of the walls to be matched to the required damping.
  • Foam is also characterized by a high energy absorption capacity.
  • the heat transfer is increased and the cooling made even more efficient. This results in a greater reduction of the temperature and thus a life extension.
  • an Invar alloy is provided as the composite.
  • This alloy has abnormally small or sometimes negative coefficients of thermal expansion in certain temperature ranges.
  • deformation can be e.g. the buckling of the boundaries, so the TBC combustion chamber side and the outside of the inner wall counteracted.
  • the height of the inner wall can be arbitrary, that is also such that it adjoins the outer wall on the combustion chamber side.
  • the TBC can be a metallic or ceramic protective layer.
  • the composite has cooling air holes. These holes can be realized as holes.
  • the cooling air holes can be placed arbitrarily deep in the composite.
  • the cooling air holes may be attached through the inner wall, for example.
  • the compressor cooling air K thus guided into the combustion chamber settles as a film between the combustion gases and the combustion chamber wall and thus produces a film cooling.
  • the composite is designed as a foam, then the compressor cooling air K can also flow away through the foam in the flow direction and thus cause efficient cooling. Therefore, the porous structure allows more efficient cooling than film cooling or impingement cooling alone because the porous structure is highly surface-enlarging. It allows a kind of transpiration cooling.
  • the diffusion flow of compressor cooling air K through the foam allows the use of a relatively small number of holes through the surface layer.
  • the inner wall may in particular have a downstream end at which the intermediate space between the outer side of the inner wall and the inner side of the outer wall is open toward the interior of the combustion chamber.
  • the cooling fluid can then be supplied to the combustion chamber interior, which is used in particular for diffusion flames.
  • compressor cooling air K or steam can be used as cooling fluid.
  • the outer wall has steps in the axial direction of the gas turbine combustor.
  • This embodiment also makes it possible to attach cooling air ducts and cooling fins between the different inner walls and the outer wall and in each case to design them differently, either with different flow cross sections and / or with different pitches of the fins and / or with different fin geometries.
  • each of the outer walls of the inner walls which are partially pushed into one another, may be fastened to a fastening section of the outer wall in their section surrounding the inner of the inner walls pushed one inside the other.
  • the inlet openings of the outer wall then adjoin these fastening sections.
  • Each intermediate space formed between an inner wall and the outer wall can then be supplied with cooling fluid individually.
  • each of the axially arranged in succession inner walls have a downstream end on which the existing between the outside of the respective inner wall and the inside of the outer wall gap to the combustion chamber interior is open.
  • a further inner wall arranged in the axial direction behind an inner wall is further cooled by means of film cooling by the compressor cooling air K entering the combustion chamber, which flows along the inside of the following inner wall.
  • the compressor cooling air K remains significantly longer in the wall designed as a composite than in the case of the planed used in the prior art or milled cooling fins. The efficiency of the cooling can be increased thereby.
  • a gas turbine according to the invention is equipped with at least one combustion chamber according to the invention.
  • a plurality of combustion chambers according to the invention for example six, eight or twelve combustion chambers, may be arranged around the rotor.
  • the advantages described with reference to the gas turbine combustor according to the invention also result in the gas turbine according to the invention. Reference is therefore made to the advantages described with reference to the gas turbine combustor according to the invention.
  • FIG. 1 shows a gas turbine 1 in a longitudinal section.
  • This comprises a compressor section 3, a combustion chamber section 5 and a turbine section 7.
  • a shaft extends through all sections of the gas turbine 1.
  • the shaft 9 is provided with rings of compressor blades 11 and in the turbine section 7 with rings of turbine blades 13.
  • Wheels of compressor vanes 15 are located in the compressor section 3 between the rotor blade rings and rings of turbine vanes 17 in the turbine section.
  • the guide vanes extend extending from the housing 19 of the gas turbine plant 1 substantially in the radial direction to the shaft.
  • FIG. 2 shows a combustion chamber 25 of the gas turbine 1 in a schematic sectional view.
  • the combustion chamber 25 includes a burner end 31 to which at least one burner 27 is disposed and through which both the fuel and compressor air are introduced into the combustion chamber.
  • the combustion chamber 25 comprises a turbine-side outlet end 33, through which the hot combustion exhaust gases exit the combustion chamber 25 in the direction of the turbine section 7.
  • the flame present in the combustion chamber 25 during operation of the gas turbine 1 results in very high temperatures in a section 35 of the combustion chamber which necessitate cooling of the combustion chamber wall, in particular when the flame is a diffusion flame.
  • the combustion chamber wall at least in this section 35, has a double-walled structure with an outer wall 37 and one or more inner walls 39A, 39B, 39C. Between the inner walls 39A, 39B, 39C and the outer wall 37 are interspaces 41A, 41B, 41C, the cooling air channels for a cooling fluid, in the present embodiment compressor cooling air K, form.
  • a cooling fluid in the present embodiment compressor cooling air K
  • the foam can be an Ivar alloy.
  • Invar is an iron-nickel alloy with 36% nickel content (FeNi36).
  • Invar alloys have the property of having abnormally small or sometimes negative coefficients of thermal expansion (CTE) in certain temperature ranges. The name thus results from the invariance of the strain with respect to a temperature change.
  • the inner walls 39 each have a mounting portion 45, in which they are attached to a mounting portion 46 of the outer wall 37.
  • the inner walls 39 have slightly different radii, wherein the radii in the flow direction 47 of the combustion gases increase.
  • the fastening portions 45 remote from the ends 40 of the inner walls 39 are inserted into a part in the downstream adjacent inner wall 39. This leaves a gap between the outside the inner inner wall (eg 39A) and the inner side of the outer Innwand (eg 39B) or the outer wall 37 so that downstream of the combustion chamber inside open annular opening 42 is formed.
  • the outer wall 37 has, in the vicinity of the fixing portions 46 to which the inner walls 39 are fixed with their fixing portions 45, through holes 49 serving as inlet openings for compressor cooling air K into the spaces 41.
  • the compressor cooling air K then flows along the outside of the inner walls 39 to cool them. Finally, the compressor cooling air K flows through the annular opening 42 into the combustion chamber interior.
  • the compressor cooling air K thus serves in the present case in several ways as compressor cooling air K, namely on the one hand by first the outside of the inner wall 39 A, 39 B, 39 C, and then the inner wall of the subsequent outer wall 37 cools.
  • the wall 39A, 39B, 39C is designed as foam, cooling by means of compressor cooling air K also takes place in the interior of the wall itself.
  • the preferably designed as a foam inner wall 39A, 39B, 39C is provided with cooling air drilling.
  • Compressor cooling air K enters this wall through the cooling air holes as well as through the pore-shaped foam structure of the inner wall 39A, 39B, 39C and flows toward the combustion chamber. Due to the pore structure, the heat transfer is substantially increased because the pore structure greatly increases the surface available for cooling.
  • the foam-formed inner wall 39A, 39B, 39C also has the advantage that it has a substantially higher rigidity than the inner wall mentioned in the prior art.
  • the foam may comprise a so-called Invar alloy, which substantially reduces the risk of deformation of the inner wall 39A, 39B, 39C due to heat.
  • the production of the composite preferably foam-made inner wall 39A, 39B, 39C is much faster than the planed in the prior art ribs. This saves time and thus costs.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09162305A 2009-06-09 2009-06-09 Chambre de combustion de turbine à gaz et turbine à gaz Withdrawn EP2270397A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09162305A EP2270397A1 (fr) 2009-06-09 2009-06-09 Chambre de combustion de turbine à gaz et turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09162305A EP2270397A1 (fr) 2009-06-09 2009-06-09 Chambre de combustion de turbine à gaz et turbine à gaz

Publications (1)

Publication Number Publication Date
EP2270397A1 true EP2270397A1 (fr) 2011-01-05

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EP09162305A Withdrawn EP2270397A1 (fr) 2009-06-09 2009-06-09 Chambre de combustion de turbine à gaz et turbine à gaz

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EP (1) EP2270397A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120167574A1 (en) * 2010-12-30 2012-07-05 Richard Christopher Uskert Gas turbine engine and combustion liner
FR3038364A1 (fr) * 2015-07-01 2017-01-06 Turbomeca Paroi de chambre de combustion
WO2020200568A1 (fr) * 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Carreau d'écran thermique à fonction d'amortissement

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4292810A (en) 1979-02-01 1981-10-06 Westinghouse Electric Corp. Gas turbine combustion chamber
WO1997014875A1 (fr) 1995-10-17 1997-04-24 Westinghouse Electric Corporation Dispositif de combustion refroidi regeneratuer pour turbine a gaz
WO1999017057A1 (fr) 1997-09-30 1999-04-08 Siemens Westinghouse Power Corporation CHAMBRE DE COMBUSTION A TRES FAIBLE EMISSION DE NO¿x?
US6495207B1 (en) * 2001-12-21 2002-12-17 Pratt & Whitney Canada Corp. Method of manufacturing a composite wall
US20050048305A1 (en) 2003-08-29 2005-03-03 General Electric Company Optical reflector for reducing radiation heat transfer to hot engine parts
US20060059916A1 (en) 2004-09-09 2006-03-23 Cheung Albert K Cooled turbine engine components

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4292810A (en) 1979-02-01 1981-10-06 Westinghouse Electric Corp. Gas turbine combustion chamber
WO1997014875A1 (fr) 1995-10-17 1997-04-24 Westinghouse Electric Corporation Dispositif de combustion refroidi regeneratuer pour turbine a gaz
WO1999017057A1 (fr) 1997-09-30 1999-04-08 Siemens Westinghouse Power Corporation CHAMBRE DE COMBUSTION A TRES FAIBLE EMISSION DE NO¿x?
US6495207B1 (en) * 2001-12-21 2002-12-17 Pratt & Whitney Canada Corp. Method of manufacturing a composite wall
US20050048305A1 (en) 2003-08-29 2005-03-03 General Electric Company Optical reflector for reducing radiation heat transfer to hot engine parts
US20060059916A1 (en) 2004-09-09 2006-03-23 Cheung Albert K Cooled turbine engine components

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120167574A1 (en) * 2010-12-30 2012-07-05 Richard Christopher Uskert Gas turbine engine and combustion liner
US9310079B2 (en) * 2010-12-30 2016-04-12 Rolls-Royce North American Technologies, Inc. Combustion liner with open cell foam and acoustic damping layers
FR3038364A1 (fr) * 2015-07-01 2017-01-06 Turbomeca Paroi de chambre de combustion
WO2020200568A1 (fr) * 2019-04-03 2020-10-08 Siemens Aktiengesellschaft Carreau d'écran thermique à fonction d'amortissement

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